EP1930455B1 - Nickel-base superalloy with excellent unsusceptibility to oxidation - Google Patents
Nickel-base superalloy with excellent unsusceptibility to oxidation Download PDFInfo
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- EP1930455B1 EP1930455B1 EP06810648.3A EP06810648A EP1930455B1 EP 1930455 B1 EP1930455 B1 EP 1930455B1 EP 06810648 A EP06810648 A EP 06810648A EP 1930455 B1 EP1930455 B1 EP 1930455B1
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- base superalloy
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- 229910000601 superalloy Inorganic materials 0.000 title claims description 28
- 230000003647 oxidation Effects 0.000 title description 28
- 238000007254 oxidation reaction Methods 0.000 title description 28
- 239000000203 mixture Substances 0.000 claims description 14
- 239000012535 impurity Substances 0.000 claims description 9
- 229910045601 alloy Inorganic materials 0.000 description 22
- 239000000956 alloy Substances 0.000 description 22
- 230000000052 comparative effect Effects 0.000 description 8
- 239000007789 gas Substances 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 238000001816 cooling Methods 0.000 description 3
- 230000001627 detrimental effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 239000006104 solid solution Substances 0.000 description 3
- 238000005728 strengthening Methods 0.000 description 3
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 239000002244 precipitate Substances 0.000 description 2
- 238000004881 precipitation hardening Methods 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 229910001173 rene N5 Inorganic materials 0.000 description 2
- 238000009864 tensile test Methods 0.000 description 2
- 229910001005 Ni3Al Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 229910052593 corundum Inorganic materials 0.000 description 1
- 230000002542 deteriorative effect Effects 0.000 description 1
- QDOXWKRWXJOMAK-UHFFFAOYSA-N dichromium trioxide Chemical compound O=[Cr]O[Cr]=O QDOXWKRWXJOMAK-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000004663 powder metallurgy Methods 0.000 description 1
- 230000001376 precipitating effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 229910001845 yogo sapphire Inorganic materials 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0433—Nickel- or cobalt-based alloys
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
Definitions
- the invention relates to a nickel-base superalloy, in more detail, to a novel nickel-base superalloy that is excellent in the oxidation resistance at high temperatures and suitable as members that are used under high temperature and high pressure such as turbine blades, turbine vanes, turbine discs and so on of jet engines, gas turbines and so on.
- a nickel-base superalloy when it is used in a base material as a turbine blade or a turbine vane of a jet engine or the like, in many cases, is used with a surface of a base material coated to inhibit high temperature oxidation and heating.
- the nickel-base superalloy is expected to be an alloy excellent in the oxidation resistance so that an apparatus may not be immediately destroyed due to oxidation and may be used until a periodic inspection.
- Rene N5 alloy an alloy made of Co: 8% by weight, Cr: 7% by weight, Mo: 2% by weight, W: 5% by weight, Al: 6.2% by weight, Ta: 7% by weight, Hf: 0.2% by weight, Re: 3% by weight and Ni as a balance
- a Rene N5 alloy an alloy made of Co: 8% by weight, Cr: 7% by weight, Mo: 2% by weight, W: 5% by weight, Al: 6.2% by weight, Ta: 7% by weight, Hf: 0.2% by weight, Re: 3% by weight and Ni as a balance
- JP2005097649 A discloses a Ni-based superalloy excellent creep characteristics at high temperature, durable against use at a temperature as high as 1150 C of the metal temperature, and suitable as a member to be used under high temperature and high stress conditions such as a turbine blade, turbine vane and turbine disk of a jet engine or a gas turbine, said superalloy having a composition comprising: ⁇ 20 wt.% of Mo; 2 to 10 wt.% of Al; ⁇ 16 wt.% of Ta+Nb+Ti; ⁇ 16 wt.% of Re; ⁇ 16 wt.% of Ru; the balance Ni and inevitable impurities.
- Patent literature 1 U. K. Patent No- GB-2235697A
- the present invention was been made in view of the above-mentioned situations and intends to provide a nickel-base superalloy that is excellent in the oxidation resistance and useful as high temperature members such as turbine blades, turbine vanes and so on of jet engines and gas turbines.
- the nickel-base superalloy of the invention is characterized by including, as means for overcoming the problems, the followings.
- alloy composition a composition consisting of Co: 0.1 to 15% by weight, Cr: 0.1 to 10% by weight, Mo: 0.1 to 4.5% by weight, W: 0.1 to 15% by weight, Al: 2 to 8% by weight, Ta + Nb + Ti: 0 to 16% by weight, Hf: 0.05 to 5% by weight, Re: 0.1 to 16% by weight, Ru: 0.1 to 16% by weight, Si: 0,4 to 2,5% by weight; said composition optionally further including singularly or in combination any one of elements of V: 3% by weight or less, Zr: 3% by weight or less, C: 0.3% by weight or less, B: 0.2% by weight or less, Y: 0.2% by weight or less, La: 0.2% by weight or less and Ce: 0.2% by weight or less; and a balance of Ni and unavoidable impurities.
- a composition includes Co: 3 to 10% by weight, Cr: 1 to 6% by weight, Mo: 0.5 to 4.5% by weight, W: 2 to 10% by weight, Al: 4 to 7% by weight, Ta + Nb + Ti: 0 to 10% by weight or less, Hf: 0.05 to 2% by weight, Re: 1 to 10% by weight, Ru: 1 to 8% by weight, Si: 0.4 to 2,5% by weight and a balance made of Ni and unavoidable impurities.
- a composition includes Co: 4 to 8% by weight, Cr: 2 to 4% by weight, Mo: 1 to 4% by weight, W: 4 to 8% by weight, Al: 4 to 7% by weight, Ta + Nb + Ti: 1 to 8% by weight, Hf: 0.05 to 0.5% by weight, Re: 3 to 8% by weight, Ru: 3 to 7% by weight, Si: 0.4 to 2.5% by weight and a balance made of Ni and unavoidable impurities.
- a turbine component such as a turbine blade, a turbine vane or the like is produced according to a standard casting process, a unidirectional solidifying process, a single crystal solidifying process, a powder metallurgy process, a forging process or the like with an alloy of any one of the first through fourth inventions.
- a nickel-base superalloy having more excellent oxidation resistance can be provided in a circumstance where, as a jet engine or a gas turbine advances, a fuel gas temperature becomes higher. So far, particularly when a fuel gas temperature is made higher, the oxidation resistance is particularly problematic. However, since the alloy of the invention is a nickel-base superalloy in which the oxidation resistance at high temperatures is taken into consideration in particular, the above-mentioned existing problems can be improved.
- a turbine blade or a turbine vane of a jet engine, a gas turbine or the like is used under high temperatures. Therefore, normally, on a surface of the member, a coating is applied to impart the heat resistance and oxidation resistance. However, when, for some reason, a coating layer is peeled, it is desirable that an exposed nickel-base superalloy may be used until a time of a next machine inspection without deteriorating within a short period due to the high temperature oxidation or the like. Furthermore, in general, since a turbine blade and a turbine vane are exposed to a high temperature, a lot of small holes are formed to apply inside cooling and cooling of a blade surface. The small holes, when these are clogged due to the high temperature oxidation, in some cases, are locally heated to be incapable of enduring the centrifugal force to collapse.
- a thickness of a member of a nickel-base superalloy becomes substantially 0.5 mm to be particularly problematic in the oxidation resistance-
- the nickel-base superalloy of the invention is excellent in the oxidation resistance; accordingly, the nickel-base superalloy, when used as a turbine blade or a turbine vane of a jet engine, a gas turbine and so on under a high temperature condition, can be used for a long time to be economically advantageous.
- the invention has features as mentioned above. Embodiments thereof will be described below.
- Co is effective in the stabilization of a structure and in an improvement in the mechanical strength-
- an amount of a gamma prime phase is reduced at high temperatures to result in a decrease in the mechanical strength; accordingly, it is set in the range of 0.1 to 15% by weight, preferably in the range of 3 to 10% by weight and most preferably in the range of 4 to 8% by weight.
- an addition amount of Cr is set in the range of 0.1 to 10% by weight. When the addition amount of Cr exceeds 10% by weight, a detrimental phase is generated to lower the high temperature strength. Accordingly, the addition amount of Cr is set preferably in the range of 1 to 6% by weight and most preferably in the range of 2 to 4% by weight.
- Mo is set in the range of 0.1 to 4.5% by weight.
- Mo forms a solid solution in a base material to elevate high temperature strength and contributes to, due to the precipitation hardening, high temperature strength.
- Mo is preferably added in the range of 0.5 to 4.5% by weight and most preferably in the range of 1 to 4% by weight.
- W has effects of, similarly to Mo, the solid-solution hardening and the precipitation hardening.
- W is added in the range of 0.1 to 15% by weight, preferably in the range of 2 to 10% by weight and most preferably in the range of 4 to 8% by weight.
- Al in combination with Ni, forms an intermetallic compound expressed by Ni 3 Al, which constitutes a gamma prime phase that precipitates in a gamma host phase, to improve the high temperature strength.
- An addition amount of Al is set in the range of 2 to 8% by weight and preferably in the range of 4 to 7% by weight.
- any one of Ta + Nb + Ti is an element that is effective in intensifying a gamma prime phase to improve the creep strength.
- a sum total thereof is 16% by weight or more, a detrimental phase is promoted to grow; accordingly, the sum total thereof is set necessarily in the range of 0 to 16% by weight, preferably in the range of 0 to 10% by weight and most preferably in the range of 1 to 8% by weight.
- Hf is effective in improving the oxidation resistance and is effectively added in an alloy of the invention.
- Hf is added necessarily 5% by weight or less, that is, necessarily in the range of 0.05 to 5% by weight, preferably in the range of 0.05 to 2% by weight and most preferably in the range of 0.05 to 0.5% by weight.
- Re dissolves in a gamma phase to improve high temperature strength due to the solid-solution strengthening. Furthermore, Re effectively improves the corrosion resistance. On the other hand, when Re is added too much, a TCP phase precipitates at high temperatures to be likely to lower the high temperature strength. Accordingly, Re is added preferably in the range of 0.1 to 16% by weight, more preferably in the range of 1 to 10% by weight and most preferably in the range of 3 to 8% by weight.
- Ru inhibits a TCP phase from precipitating to improve the high temperature strength.
- a composition ratio of Ru is preferably in the range of 0.1 to 16% by weight, preferably in the range of 1 to 8% by weight and most preferably in the range of 3 to 7% by weight.
- Si is an element that forms a protective oxide film such as Al 2 O 3 on an alloy surface to improve the oxidation resistance.
- Si is added much, the solubility limits of other elements are lowered; accordingly, Si is added necessarily in the range of 0.4 to 2.5% by weight.
- V is an element that dissolves in a gamma prime phase to strengthen the gamma prime phase-
- an addition amount of V is specified to 3% by weight or less.
- Zr is an element that strengthens a grain boundary similarly to B and C. However, when Zr is added too much, the creep strength is lowered; accordingly, an addition amount of Zr is specified to 3% by weight or less.
- C contributes to grain boundary strengthening.
- an addition amount of C is specified to 0.3% by weight or less.
- B similarly to C, contributes to grain boundary strengthening.
- an addition amount of B is specified to 0.2% by weight or less.
- Y, La or Ce are elements that improve the adhesiveness of a protective oxide film that forms alumina, chromia or the like when a nickel-base superalloy is used at high temperatures.
- Y is specified to be 0.2% by weight or less
- La is specified to be 0.2% by weight or less
- Ce is specified to be 0.2% by weight or less.
- a nickel-base superalloy of the invention which is mentioned above and excellent in the oxidation resistance, in consideration of procedures and conditions of so far known producing processes, can be produced by conventional cast alloy, a directionally solidified alloy, a single crystal superalloy and so on.
- the oxidation resistance test was carried out in air at a test temperature of 1100°C.
- the sample was, after holding at the test temperature for 1 hr, taken out of a furnace.
- the sample was cooled and a weight change thereof was measured. Thereafter, the sample was repeated to measure, after holding once more at the test temperature for 1 hr, a weight change.
- the tensile test was carried out at 400°C of example 1 and comparative example 2. As the results thereof, as shown in Fig. 2 , the superalloy of the invention had the mechanical strength more excellent than that of comparative example 2 in both of the 0.2% proof stress and the tensile strength.
- a nickel-base alloy that does not contain Si but contains Co: 5.8% by weight, Cr: 3.2% by weight, Mo: 2.8% by weight, W: 5.6% by weight, Al: 5.7% by weight, Hf: 0.1% by weight, Re: 5.8% by weight, Ru: 3.6% by weight, Ta: 5.6% by weight and a balance made of Ni and unavoidable impurities was melted.
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Description
- The invention relates to a nickel-base superalloy, in more detail, to a novel nickel-base superalloy that is excellent in the oxidation resistance at high temperatures and suitable as members that are used under high temperature and high pressure such as turbine blades, turbine vanes, turbine discs and so on of jet engines, gas turbines and so on.
- A nickel-base superalloy, when it is used in a base material as a turbine blade or a turbine vane of a jet engine or the like, in many cases, is used with a surface of a base material coated to inhibit high temperature oxidation and heating. In this connection, even when the coating is peeled off for some reason, the nickel-base superalloy is expected to be an alloy excellent in the oxidation resistance so that an apparatus may not be immediately destroyed due to oxidation and may be used until a periodic inspection.
- Among conventional nickel-base superalloys, a Rene N5 alloy (an alloy made of Co: 8% by weight, Cr: 7% by weight, Mo: 2% by weight, W: 5% by weight, Al: 6.2% by weight, Ta: 7% by weight, Hf: 0.2% by weight, Re: 3% by weight and Ni as a balance) is known as an alloy excellent in the oxidation resistance (see patent literature 1).
-
JP2005097649 A - However, with a recent advance in jet engines and gas turbines, a fuel gas temperature becomes further higher. Accordingly, a nickel-base superalloy having further excellent oxidation resistance is expected to realize.
Patent literature 1: U. K. Patent No-GB-2235697A - The present invention was been made in view of the above-mentioned situations and intends to provide a nickel-base superalloy that is excellent in the oxidation resistance and useful as high temperature members such as turbine blades, turbine vanes and so on of jet engines and gas turbines.
- The nickel-base superalloy of the invention is characterized by including, as means for overcoming the problems, the followings.
- Firstly, as an alloy composition, a composition consisting of Co: 0.1 to 15% by weight, Cr: 0.1 to 10% by weight, Mo: 0.1 to 4.5% by weight, W: 0.1 to 15% by weight, Al: 2 to 8% by weight, Ta + Nb + Ti: 0 to 16% by weight, Hf: 0.05 to 5% by weight, Re: 0.1 to 16% by weight, Ru: 0.1 to 16% by weight, Si: 0,4 to 2,5% by weight;
said composition optionally further including singularly or in combination any one of elements of V: 3% by weight or less, Zr: 3% by weight or less, C: 0.3% by weight or less, B: 0.2% by weight or less, Y: 0.2% by weight or less, La: 0.2% by weight or less and Ce: 0.2% by weight or less;
and a balance of Ni and unavoidable impurities. - Secondly, in the alloy of the first invention, a composition includes Co: 3 to 10% by weight, Cr: 1 to 6% by weight, Mo: 0.5 to 4.5% by weight, W: 2 to 10% by weight, Al: 4 to 7% by weight, Ta + Nb + Ti: 0 to 10% by weight or less, Hf: 0.05 to 2% by weight, Re: 1 to 10% by weight, Ru: 1 to 8% by weight, Si: 0.4 to 2,5% by weight and a balance made of Ni and unavoidable impurities.
- Thirdly, in the alloy of the first invention, a composition includes Co: 4 to 8% by weight, Cr: 2 to 4% by weight, Mo: 1 to 4% by weight, W: 4 to 8% by weight, Al: 4 to 7% by weight, Ta + Nb + Ti: 1 to 8% by weight, Hf: 0.05 to 0.5% by weight, Re: 3 to 8% by weight, Ru: 3 to 7% by weight, Si: 0.4 to 2.5% by weight and a balance made of Ni and unavoidable impurities.
- Fourthly, a turbine component such as a turbine blade, a turbine vane or the like is produced according to a standard casting process, a unidirectional solidifying process, a single crystal solidifying process, a powder metallurgy process, a forging process or the like with an alloy of any one of the first through fourth inventions.
- According to the invention, in a circumstance where, as a jet engine or a gas turbine advances, a fuel gas temperature becomes higher, a nickel-base superalloy having more excellent oxidation resistance can be provided. So far, particularly when a fuel gas temperature is made higher, the oxidation resistance is particularly problematic. However, since the alloy of the invention is a nickel-base superalloy in which the oxidation resistance at high temperatures is taken into consideration in particular, the above-mentioned existing problems can be improved.
- A turbine blade or a turbine vane of a jet engine, a gas turbine or the like is used under high temperatures. Therefore, normally, on a surface of the member, a coating is applied to impart the heat resistance and oxidation resistance. However, when, for some reason, a coating layer is peeled, it is desirable that an exposed nickel-base superalloy may be used until a time of a next machine inspection without deteriorating within a short period due to the high temperature oxidation or the like. Furthermore, in general, since a turbine blade and a turbine vane are exposed to a high temperature, a lot of small holes are formed to apply inside cooling and cooling of a blade surface. The small holes, when these are clogged due to the high temperature oxidation, in some cases, are locally heated to be incapable of enduring the centrifugal force to collapse.
- Furthermore, owing to the inside cooling, in some cases, a thickness of a member of a nickel-base superalloy becomes substantially 0.5 mm to be particularly problematic in the oxidation resistance- The nickel-base superalloy of the invention is excellent in the oxidation resistance; accordingly, the nickel-base superalloy, when used as a turbine blade or a turbine vane of a jet engine, a gas turbine and so on under a high temperature condition, can be used for a long time to be economically advantageous.
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- [
Fig. 1] Fig. 1 is a diagram showing results of oxidation tests (repetition of heating at 1100°C and holding there for 1 hr in air) of examples 1 through 3. - [
Fig. 2] Fig. 2 is a diagram showing results of tensile tests at a test temperature of 400°C of examples 1 and 2. - [
Fig. 3] Fig. 3 is a diagram showing results of oxidation tests (repetition of heating at 1100°C and holding there for 1 hr in air) of example 4. - The invention has features as mentioned above. Embodiments thereof will be described below.
- Limiting reasons of an alloy element composition of a nickel-base superalloy of the invention is as follows.
- In the beginning, Co is effective in the stabilization of a structure and in an improvement in the mechanical strength- However, when Co is added more than 15% by weight, an amount of a gamma prime phase is reduced at high temperatures to result in a decrease in the mechanical strength; accordingly, it is set in the range of 0.1 to 15% by weight, preferably in the range of 3 to 10% by weight and most preferably in the range of 4 to 8% by weight.
- In the next place, Cr is effective in an improvement in the corrosion resistance. An addition amount of Cr is set in the range of 0.1 to 10% by weight. When the addition amount of Cr exceeds 10% by weight, a detrimental phase is generated to lower the high temperature strength. Accordingly, the addition amount of Cr is set preferably in the range of 1 to 6% by weight and most preferably in the range of 2 to 4% by weight.
- Then, Mo is set in the range of 0.1 to 4.5% by weight. Mo forms a solid solution in a base material to elevate high temperature strength and contributes to, due to the precipitation hardening, high temperature strength. Mo is preferably added in the range of 0.5 to 4.5% by weight and most preferably in the range of 1 to 4% by weight.
- Next, W has effects of, similarly to Mo, the solid-solution hardening and the precipitation hardening. W is added in the range of 0.1 to 15% by weight, preferably in the range of 2 to 10% by weight and most preferably in the range of 4 to 8% by weight.
- Then, Al, in combination with Ni, forms an intermetallic compound expressed by Ni3Al, which constitutes a gamma prime phase that precipitates in a gamma host phase, to improve the high temperature strength. An addition amount of Al is set in the range of 2 to 8% by weight and preferably in the range of 4 to 7% by weight.
- In the next place, any one of Ta + Nb + Ti is an element that is effective in intensifying a gamma prime phase to improve the creep strength. In any case, when a sum total thereof is 16% by weight or more, a detrimental phase is promoted to grow; accordingly, the sum total thereof is set necessarily in the range of 0 to 16% by weight, preferably in the range of 0 to 10% by weight and most preferably in the range of 1 to 8% by weight.
- Then, Hf is effective in improving the oxidation resistance and is effectively added in an alloy of the invention. However, when Hf is added exceeding 5% by weight, a detrimental phase is promoted to grow; accordingly, Hf is added necessarily 5% by weight or less, that is, necessarily in the range of 0.05 to 5% by weight, preferably in the range of 0.05 to 2% by weight and most preferably in the range of 0.05 to 0.5% by weight.
- Next, Re dissolves in a gamma phase to improve high temperature strength due to the solid-solution strengthening. Furthermore, Re effectively improves the corrosion resistance. On the other hand, when Re is added too much, a TCP phase precipitates at high temperatures to be likely to lower the high temperature strength. Accordingly, Re is added preferably in the range of 0.1 to 16% by weight, more preferably in the range of 1 to 10% by weight and most preferably in the range of 3 to 8% by weight.
- Then, Ru inhibits a TCP phase from precipitating to improve the high temperature strength. A composition ratio of Ru is preferably in the range of 0.1 to 16% by weight, preferably in the range of 1 to 8% by weight and most preferably in the range of 3 to 7% by weight.
- In the next place, Si is an element that forms a protective oxide film such as Al2O3 on an alloy surface to improve the oxidation resistance. When Si is added much, the solubility limits of other elements are lowered; accordingly, Si is added necessarily in the range of 0.4 to 2.5% by weight.
- Then, V is an element that dissolves in a gamma prime phase to strengthen the gamma prime phase- However, when V is added too much, the creep strength is lowered; accordingly, an addition amount of V is specified to 3% by weight or less.
- Next, Zr is an element that strengthens a grain boundary similarly to B and C. However, when Zr is added too much, the creep strength is lowered; accordingly, an addition amount of Zr is specified to 3% by weight or less.
- In the next place, C contributes to grain boundary strengthening. However, when C is added too much, the ductility is damaged; accordingly, an addition amount of C is specified to 0.3% by weight or less.
- Then, B, similarly to C, contributes to grain boundary strengthening. However, when B is added too much, the ductility is damaged; accordingly, an addition amount of B is specified to 0.2% by weight or less.
- Next, Y, La or Ce are elements that improve the adhesiveness of a protective oxide film that forms alumina, chromia or the like when a nickel-base superalloy is used at high temperatures. However, when these are used too much, the solubility limits of other elements are lowered; accordingly, Y is specified to be 0.2% by weight or less, La is specified to be 0.2% by weight or less, and Ce is specified to be 0.2% by weight or less.
- A nickel-base superalloy of the invention, which is mentioned above and excellent in the oxidation resistance, in consideration of procedures and conditions of so far known producing processes, can be produced by conventional cast alloy, a directionally solidified alloy, a single crystal superalloy and so on.
- In what follows, examples will be described. It goes without saying that the invention is not restricted to the examples below.
- In the beginning, nickel-base alloys having the respective compositions shown in Table 1 were melted.
[Table 1] Composition (Ni: Bal. % by weight) Co Cr Mo W Al Hf Re Ru Ta Si Example 1 5.8 2.9 2.9 5.8 5.8 0.1 7.2 5.2 0 1.9 Example 2 5.8 2.9 2.9 5.8 5.8 0.1 7.1 5.2 1.4 1.4 Example 3 5.7 2.8 2.8 5.7 5.7 0.1 7.0 5.1 2.8 1.0 Comparative Example 1 5.6 2.8 2.8 5.6 5.6 0.1 6.9 5.0 5.6 0 Comparative Example 2 8.0 7.0 2.0 5.0 6.2 0.2 3.0 0 7.0 0 - With each of the obtained alloys, a sample having a diameter of 9 mmφ and a height of 5 mm was prepared. The samples were used to evaluate the oxidation resistance.
- The oxidation resistance test was carried out in air at a test temperature of 1100°C. The sample was, after holding at the test temperature for 1 hr, taken out of a furnace. The sample was cooled and a weight change thereof was measured. Thereafter, the sample was repeated to measure, after holding once more at the test temperature for 1 hr, a weight change.
- As the result, as shown in
Fig. 1 , within a range of 50 times of the number of tests, in examples 1, 2 and 3, which contain Si, noble nickel-base superalloys that have the oxidation resistance exceeding that of a comparative alloy 2 (Rene N5) that has been said excellent in the oxidation resistance were found. Thecomparative alloy 1 that does not contain Si is poor in the oxidation resistance. - The tensile test was carried out at 400°C of example 1 and comparative example 2. As the results thereof, as shown in
Fig. 2 , the superalloy of the invention had the mechanical strength more excellent than that of comparative example 2 in both of the 0.2% proof stress and the tensile strength. - As an example 4, a nickel-base alloy made of Co: 5.8% by weight, Cr. 3.2% by weight, Mo: 2.8% by weight, W: 5.6% by weight, Al: 5.7% by weight, Hf: 0.1% by weight, Re: 5.8% by weight, Ru: 3.6% by weight, Ta: 5.6% by weight, Si: 0.45% by weight and a balance made of Ni and unavoidable impurities was melted. As a
comparative alloy 3, a nickel-base alloy that does not contain Si but contains Co: 5.8% by weight, Cr: 3.2% by weight, Mo: 2.8% by weight, W: 5.6% by weight, Al: 5.7% by weight, Hf: 0.1% by weight, Re: 5.8% by weight, Ru: 3.6% by weight, Ta: 5.6% by weight and a balance made of Ni and unavoidable impurities was melted. - The oxidation resistance test similar to that of examples 1 through 3 was carried out. As shown in
Fig. 3 , also in the nickel-base superalloy that contains 0.45% by weight of Si, in comparison withcomparative alloy 3 that does not contain Si, the oxidation resistance was considerably improved
Claims (4)
- A nickel-base superalloy, characterized by having a composition that consists of Co: 0.1 to 15% by weight, Cr: 0.1 to 10% by weight, Mo: 0.1 to 4.5% by weight, W: 0.1 to 15% by weight, Al: 2 to 8% by weight, Ta + Nb + Ti: 0 to 16% by weight, Hf: 0.05 to 5% by weight, Re: 0.1 to 16% by weight, Ru: 0.1 to 16% by weight, Si: 0.4 to 2.5% by weight;
said composition optionally further including singularly or in combination any one of elements of V: 3% by weight or less, Zr: 3% by weight or less, C: 0.3% by weight or less, B: 0.2% by weight or less, Y: 0.2% by weight or less, La: 0.2% by weight or less and Ce: 0.2% by weight or less;
and a balance of Ni and unavoidable impurities. - The nickel-base superalloy of claim 1, characterized by having a composition that includes Co: 3 to 10% by weight, Cr: 1 to 6% by weight, Mo: 0.5 to 4.5% by weight, W: 2 to 10% by weight, Al: 4 to 7% by weight, Ta + Nb + Ti: 0 to 10% by weight or less, Hf: 0.05 to 2% by weight. Re: 1 to 10% by weight, Ru: 1 to 8% by weight, Si: 0.4 to 2,5% by weight and a balance made of Ni and unavoidable impurities.
- The nickel-base superalloy of claim 1, characterized by having a composition that includes Co: 4 to 8% by weight, Cr: 2 to 4% by weight, Mo: 1 to 4% by weight, W: 4 to 8% by weight, Al: 4 to 7% by weight, Ta + Nb + Ti: 1 to 8% by weight, Hf: 0.05 to 0.5% by weight, Re: 3 to 8% by weight, Ru: 3 to 7% by weight, Si: 0.4 to 2.5% by weight and a balance made of Ni and unavoidable impurities.
- A turbine component such as a turbine blade, a turbine vane or the like, produced from a superalloy as claimed in any one of claims 1 to 3.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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JP2005280993 | 2005-09-27 | ||
PCT/JP2006/319183 WO2007037277A1 (en) | 2005-09-27 | 2006-09-27 | Nickel-base superalloy with excellent unsusceptibility to oxidation |
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EP1930455A1 EP1930455A1 (en) | 2008-06-11 |
EP1930455A4 EP1930455A4 (en) | 2010-01-13 |
EP1930455B1 true EP1930455B1 (en) | 2013-07-03 |
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EP06810648.3A Active EP1930455B1 (en) | 2005-09-27 | 2006-09-27 | Nickel-base superalloy with excellent unsusceptibility to oxidation |
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US (1) | US8926897B2 (en) |
EP (1) | EP1930455B1 (en) |
JP (1) | JP5344453B2 (en) |
WO (1) | WO2007037277A1 (en) |
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- 2006-09-27 JP JP2007537644A patent/JP5344453B2/en active Active
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EP1930455A1 (en) | 2008-06-11 |
JP5344453B2 (en) | 2013-11-20 |
WO2007037277A1 (en) | 2007-04-05 |
US8926897B2 (en) | 2015-01-06 |
EP1930455A4 (en) | 2010-01-13 |
JPWO2007037277A1 (en) | 2009-04-09 |
US20090196760A1 (en) | 2009-08-06 |
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